EP 1484476 A2 20041208 - Cooled platform for a turbine nozzle guide vane or rotor blade
Title (en)
Cooled platform for a turbine nozzle guide vane or rotor blade
Title (de)
Kühlung der Plattform einer Gasturbinenlaufschaufel oder -leitschaufel
Title (fr)
Refroidissement de la plate-forme d'une aube ou d'une aube de guidage de turbine
Publication
Application
Priority
GB 0312867 A 20030604
Abstract (en)
A turbine aerofoil (20) for a gas turbine has a pressure wall (26) and suction wall (28) and at least one internal cavity (24). An aerofoil platform (16,18) adjacent and generally perpendicular to the aerofoil has at least one internal cavity (41) with a pressure wall (42) and suction wall (44) on respective sides of the cavity. The cavity (41) is divided into at least two cooling chambers (48,50) including a first chamber (48) for receiving cooling air for the platform pressure wall and a second chamber (50) for receiving cooling air for cooling the platform suction wall. The first chamber is in flow communication with the aerofoil cavity for discharge of at least part of the cooling air entering the first chamber to the aerofoil cavity.
IPC 1-7
IPC 8 full level
B63H 1/14 (2006.01); F01D 5/18 (2006.01); F01D 9/02 (2006.01); F01D 9/04 (2006.01)
CPC (source: EP GB US)
F01D 5/183 (2013.01 - GB); F01D 5/187 (2013.01 - EP US); F01D 5/188 (2013.01 - GB); F01D 9/02 (2013.01 - GB); F01D 9/041 (2013.01 - EP US); F05D 2240/81 (2013.01 - EP US); F05D 2260/201 (2013.01 - EP US)
Designated contracting state (EPC)
DE FR
DOCDB simple family (publication)
EP 1484476 A2 20041208; EP 1484476 A3 20070523; EP 1484476 B1 20160608; GB 0312867 D0 20030709; GB 2402442 A 20041208; GB 2402442 B 20060531; US 2004247435 A1 20041209; US 7001141 B2 20060221
DOCDB simple family (application)
EP 04252296 A 20040419; GB 0312867 A 20030604; US 83011004 A 20040423